Turbine airfoil turbulator arrangement

Patent metadata

Field	Value
Publication number	US-9995146-B2
Application number	US-201514699607-A
Country	US
Kind code	B2
Filing date	Apr 29, 2015
Priority date	Apr 29, 2015
Publication date	Jun 12, 2018
Grant date	Jun 12, 2018

Abstract

A turbine airfoil includes a leading edge and a trailing edge. Also included is a cooling channel extending in a radial direction and tapering inwardly toward the trailing edge, the cooling channel at least partially defined by a pressure side face and a suction side face. Further included is a first plurality of turbulators protruding from one of the pressure side face and the suction side face to define a first height, the first plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other. Yet further included is a second plurality of turbulators protruding from one of the pressure side face and the suction side face to define a second height that is less than the first height, the second plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other.

First claim

What is claimed is:

1. A turbine airfoil comprising:
a leading edge;
a trailing edge;
a cooling channel extending in a radial direction from a root portion to a tip portion and tapering inwardly as the cooling channel extends toward the trailing edge, the cooling channel at least partially defined by a pressure side face and a suction side face;
a first plurality of turbulators disposed in the cooling channel and protruding from one of the pressure side face and the suction side face to define a first height, the first plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other; and
a second plurality of turbulators disposed in the cooling channel and protruding from one of the pressure side face and the suction side face to define a second height that is less than the first height, the second plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other.

2. The turbine airfoil of claim 1 , wherein a cooling air is routed through the cooling channel along a main flow direction, at least one of the first plurality of turbulators and the second plurality of turbulators oriented parallel to the main flow direction.

3. The turbine airfoil of claim 1 , wherein a cooling air is routed through the cooling channel along a main flow direction, at least one of the first plurality of turbulators and the second plurality of turbulators oriented perpendicularly to the main flow direction.

4. The turbine airfoil of claim 1 , wherein a cooling air is routed through the cooling channel along a main flow direction, at least one of the first plurality of turbulators and the second plurality of turbulators oriented at an angle to the main flow direction.

5. The turbine airfoil of claim 1 , wherein the first plurality of turbulators are all oriented at a first angle and the second plurality of turbulators are all disposed at a second angle that is distinct from the first angle.

6. The turbine airfoil of claim 1 , wherein the first plurality of turbulators and the second plurality of turbulators are all oriented at the same angle.

7. The turbine airfoil of claim 1 , wherein each of the first plurality of turbulators include a trailing end and each of the second plurality of turbulators include a leading end, wherein the trailing end of each of the first plurality of turbulators and the leading end of each of the second plurality of turbulators are located within a common plane.

8. The turbine airfoil of claim 1 , wherein each of the first plurality of turbulators include a trailing end and each of the second plurality of turbulators include a leading end, and where the trailing end and the leading end are located in an overlapping arrangement.

9. The turbine airfoil of claim 1 , wherein the first plurality of turbulators are radially aligned with the second plurality of turbulators.

10. The turbine airfoil of claim 1 , wherein the first plurality of turbulators are radially misaligned with the second plurality of turbulators to form a staggered arrangement.

11. The turbine airfoil of claim 1 , wherein at least one of the first plurality of turbulators is radially aligned with one of the second plurality of turbulators and at least one of the first plurality of turbulators is radially misaligned with the second plurality of turbulators.

12. The turbine airfoil of claim 1 , wherein each pair of adjacent turbulators of the first plurality of turbulators comprises a first pitch and each of the first plurality of turbulators includes a first height, each pair of adjacent turbulators of the second plurality of turbulators comprises a second pitch and each of the second plurality of turbulators includes a second height, wherein the second pitch is less than the first pitch and the second height is less than the first height.

13. The turbine airfoil of claim 12 , further comprising a first ratio defined by the first pitch divided by the first height and a second ratio defined by the second pitch divided by the second height, wherein the first ratio and the second ratio are each within a range of 7-12.

14. The turbine airfoil of claim 1 , wherein the first plurality of turbulators and the second plurality of turbulators protrude from the suction side face, the turbine airfoil further comprising:
a third plurality of turbulators disposed in the cooling channel and protruding from the pressure side face to define a third height, the third plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other; and
a fourth plurality of turbulators disposed in the cooling channel and protruding from the pressure side face to define a fourth height that is less than the third height, the fourth plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other.

15. The turbine airfoil of claim 14 , wherein the third plurality of turbulators are radially aligned with the first plurality of turbulators and the fourth plurality of turbulators are radially aligned with the second plurality of turbulators.

16. The turbine airfoil of claim 14 , wherein the third plurality of turbulators are radially misaligned with the first plurality of turbulators and the fourth plurality of turbulators are radially misaligned with the second plurality of turbulators.

17. A gas turbine engine comprising:
a compressor section;
a combustor section; and
a turbine section having a turbine airfoil comprising:
a leading edge;
a trailing edge;
a cooling channel extending in a radial direction from a root portion to a tip portion and tapering inwardly as the cooling channel extends toward the trailing edge, the cooling channel at least partially defined by a pressure side face and a suction side face;
a first plurality of turbulators disposed in the cooling channel and protruding from the suction side face to define a first height, the first plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other;
a second plurality of turbulators disposed in the cooling channel and protruding from the suction side face to define a second height that is less than the first height, the second plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other;
a third plurality of turbulators disposed in the cooling channel and protruding from the pressure side face to define a third height, the third plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other; and
a fourth plurality of turbulators disposed in the cooling channel and protruding from the pressure side face to define a fourth height that is less than the third height, the fourth plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other.

18. The gas turbine engine of claim 17 , wherein the first plurality of turbulators are oriented at a first angle and the second plurality of turbulators are disposed at a second angle that is distinct from the first angle.

19. The gas turbine engine of claim 17 , wherein each of the first plurality of turbulators include a trailing end and the second plurality of turbulators include a leading end, the trailing end and the leading end spaced from each other.

20. The gas turbine engine of claim 17 , wherein each pair of adjacent turbulators of the fi

Assignees

• Gen Electric

Inventors

• Benson Adebukola Oluwaseun
• Hogberg Nicholas Alvin
• Itzel Gary Michael
• Merrill Mitchell Allan
• Zhang Xiuzhang James

Classifications

• F05D2260/2212

  by creating turbulence · CPC title

• F05D2240/127

  Vortex generators, turbulators, or the like, for mixing · CPC title

• F05D2260/22141

  using fins or ribs · CPC title

• F01D5/18 Primary

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title